CN117072346A - Device for connecting combustion chamber and injector in thrust chamber - Google Patents
Device for connecting combustion chamber and injector in thrust chamber Download PDFInfo
- Publication number
- CN117072346A CN117072346A CN202311337307.6A CN202311337307A CN117072346A CN 117072346 A CN117072346 A CN 117072346A CN 202311337307 A CN202311337307 A CN 202311337307A CN 117072346 A CN117072346 A CN 117072346A
- Authority
- CN
- China
- Prior art keywords
- combustion chamber
- sleeve
- injector
- connecting piece
- chamber
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 238000002485 combustion reaction Methods 0.000 title claims abstract description 68
- 239000007769 metal material Substances 0.000 claims abstract description 18
- 239000000463 material Substances 0.000 claims abstract description 11
- 238000007789 sealing Methods 0.000 claims abstract description 11
- 238000010894 electron beam technology Methods 0.000 claims description 4
- 238000000034 method Methods 0.000 abstract description 7
- 238000003466 welding Methods 0.000 abstract description 7
- 230000008602 contraction Effects 0.000 abstract description 3
- 229910052755 nonmetal Inorganic materials 0.000 abstract description 3
- 238000005516 engineering process Methods 0.000 abstract description 2
- 238000002844 melting Methods 0.000 abstract description 2
- 230000008018 melting Effects 0.000 abstract description 2
- 239000007788 liquid Substances 0.000 description 4
- 239000002184 metal Substances 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 239000007787 solid Substances 0.000 description 2
- 239000002131 composite material Substances 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000002737 fuel gas Substances 0.000 description 1
- 239000007789 gas Substances 0.000 description 1
- 230000017525 heat dissipation Effects 0.000 description 1
- 239000003380 propellant Substances 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/60—Constructional parts; Details not otherwise provided for
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/44—Feeding propellants
- F02K9/52—Injectors
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/60—Constructional parts; Details not otherwise provided for
- F02K9/62—Combustion or thrust chambers
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T10/00—Road transport of goods or passengers
- Y02T10/10—Internal combustion engine [ICE] based vehicles
- Y02T10/12—Improving ICE efficiencies
Abstract
The utility model discloses a connecting device for a combustion chamber and an injector in a thrust chamber, wherein the combustion chamber made of non-metal materials is connected with the injector made of metal materials, the connecting end of the combustion chamber with a contraction channel is provided with a connecting lug, the combustion chamber is connected with the injector through a sleeve front connecting piece, the sleeve front connecting piece is sleeved outside the connecting lug of the combustion chamber by the front end of the combustion chamber, the sleeve rear connecting piece is sleeved at the rear side of the connecting lug of the combustion chamber by the rear end of the combustion chamber, and the sleeve front connecting piece is fixedly connected with the sleeve rear connecting piece. The utility model realizes the technology of welding the nonmetallic material combustion chamber and the metallic material injector, greatly reduces the welding difficulty between materials with different melting points, and can realize the sealing effect, so that the risk of high-temperature gas leakage can not be generated in the working process of the combustion chamber.
Description
Technical Field
The present utility model relates to a connecting device, and more particularly, to a connecting device for connecting a combustion chamber and an injector in a thrust chamber.
Background
The thrust chamber is a component of the rocket engine for converting the energy of the propellant and generating the thrust. The method is divided into a solid rocket engine and a liquid rocket engine. The thrust chamber of a solid rocket engine is the engine itself. The thrust chamber of the liquid rocket engine consists of an injector, a combustion chamber and a spray pipe.
The injector of the thrust chamber of the liquid rocket engine is welded with the combustion chamber, and the existing injector and the combustion chamber are generally made of metal materials and are easy to weld together. However, in the working process of the thrust chamber of the rocket engine, the high temperature resistant material is needed because of the high temperature of the combustion chamber, the injector does not need to be as high temperature resistant as the combustion chamber, and if the combustion chamber is made of a nonmetallic material with higher heat resistant temperature, the combustion chamber and the injector cannot be directly welded together.
The utility model patent with the application number of 202223410752.4 and the application name of rocket engine thrust chamber discloses a thrust chamber which solves the problem of poor heat dissipation effect and does not provide a technical scheme for solving the problem of connection between an injector and a combustion chamber.
The utility model patent with the application number 202210797681.3 and the application name of a connecting structure and a connecting method of a composite material plate and a metal connecting piece discloses a structure and a method for connecting a nonmetallic material and a metal material, which mainly adopt embedded connection and are not suitable for connecting an injector of a thrust chamber of a liquid rocket engine with a combustion chamber.
Disclosure of Invention
Aiming at the defects of the prior art, the utility model provides the connecting device, which solves the problem that the connecting mode of the combustion chamber and the injector with different materials in the thrust chamber is adopted, and the connecting piece ensures the sealing performance, so that high-temperature fuel gas cannot leak to the outside through the connecting piece when the combustion chamber works, and the danger is avoided.
The connecting device for the combustion chamber and the injector in the thrust chamber is characterized in that the combustion chamber made of non-metal materials is connected with the injector made of metal materials, the connecting end of the combustion chamber with a contraction type channel is provided with a connecting lug, the combustion chamber is connected with the injector through a front connecting piece of a sleeve, the front connecting piece of the sleeve is sleeved outside the connecting lug of the combustion chamber by the front end of the combustion chamber, the rear connecting piece of the sleeve is sleeved at the rear side of the connecting lug of the combustion chamber by the rear end of the combustion chamber, and the front connecting piece of the sleeve is fixedly connected with the rear connecting piece of the sleeve.
Further optimized, the front connecting piece of the sleeve is made of metal material, and the rear connecting piece of the sleeve is made of metal material.
Further preferably, the front connecting piece of the sleeve and the rear connecting piece of the sleeve are welded by electron beams.
Further preferably, a sealing ring is arranged between the connecting lug and the front connecting sheet of the sleeve.
Further optimized, the section of the front connecting piece of the sleeve is -shaped, the upper part and the lower part of the front connecting piece of the -shaped sleeve are side walls, the side walls are sleeved on the outer sides of the connecting lugs, the left side is an end piece, and the end piece is annular; the rear connecting piece of the sleeve is annular.
Further optimizing, in order to ensure the reliability of the integral connection, the difference between the outer circle radius and the inner circle radius of the rear connecting piece of the sleeve is larger than the wall thickness of the edge of the front connecting piece of the sleeve.
The utility model has the advantages that: the utility model realizes the technology of welding the nonmetallic material combustion chamber and the metallic material injector, greatly reduces the welding difficulty between materials with different melting points, and can realize the sealing effect, so that the risk of high-temperature gas leakage can not be generated in the working process of the combustion chamber.
Drawings
FIG. 1 is a schematic diagram of the connection assembly of a combustion chamber with an injector in a thrust chamber;
FIG. 2 is an exploded view of the combustion chamber and injector connection arrangement in the thrust chamber;
FIG. 3 is an enlarged schematic view of the junction of the combustion chamber and the injector connection in the thrust chamber.
Reference numerals: the device comprises a 1-sleeve front connecting piece, a 2-sealing ring, a 3-combustion chamber, a 4-sleeve rear connecting piece and a connecting part between the 5-sleeve front connecting piece and the sleeve rear connecting piece.
Detailed Description
A device for connecting a combustion chamber to an injector in a thrust chamber is further described with reference to the accompanying drawings.
As shown in fig. 1-3, in the connecting device of the combustion chamber and the injector in the thrust chamber, the combustion chamber 3 made of non-metal materials is connected with the injector made of metal materials, the connecting end of the combustion chamber 3 with a contraction channel is provided with a connecting lug, the combustion chamber 3 is connected with the injector through a metal sleeve front connecting piece 1, the sleeve front connecting piece 1 is sleeved outside the connecting lug of the combustion chamber 3 by the front end of the combustion chamber 3, the sleeve rear connecting piece 4 is sleeved at the rear side of the connecting lug of the combustion chamber 3 by the rear end of the combustion chamber 3, and the connecting part 5 of the sleeve front connecting piece and the sleeve rear connecting piece adopts electron beam welding. The front connecting piece 1 of the sleeve is made of metal material, and the rear connecting piece 4 of the sleeve is made of metal material. In order to enhance the air tightness in the combustion chamber 3, a sealing ring 2 is arranged between the connecting lug and the front connecting piece 1 of the sleeve. The section of the sleeve front connecting sheet 1 is -shaped, the upper part and the lower part of the -shaped sleeve front connecting sheet are side walls, the side walls are sleeved on the outer sides of the connecting lugs, the left side is an end sheet, and the end sheet is annular; the rear connecting piece of the sleeve is annular. In order to ensure the reliability of the integral connection, the difference between the outer circle radius and the inner circle radius of the rear connecting piece of the sleeve is larger than the wall thickness of the edge of the front connecting piece of the sleeve.
The sleeve rear connecting piece 4 is sleeved at the connecting lug of the combustion chamber 3 from the rear end of the combustion chamber 3, then the sealing ring 2 is sleeved on the outer circumferential surface of the connecting lug at the front end of the combustion chamber 3 to be used as sealing, finally the sleeve front connecting piece 1 is sleeved outside the sealing ring 2 at the front end of the combustion chamber 3, electron beam welding is carried out at the connecting part 5 between the sleeve front connecting piece and the sleeve rear connecting piece as shown in fig. 1 and 3, and the sleeve front connecting piece 1 and the sleeve rear connecting piece 4 are welded together.
If the temperature of the combustion chamber 3 in a certain thrust chamber is too high and a high-temperature-resistant nonmetallic material is adopted, the combustion chamber 3 and the injector cannot be directly welded, and the connecting device is easy to realize the welding process of the injector and the combustion chamber 3 because the connecting structure is only that the inner sealing ring 2 is made of the nonmetallic material and the parts which are connected with the injector are made of the metallic materials.
The foregoing has shown and described the basic principles, principal structures and advantages of the utility model. It will be appreciated by those skilled in the art that variations and modifications in size and orientation, etc. may be made to the utility model without departing from the spirit and scope of the utility model, and that such variations and modifications are within the scope of the utility model as claimed.
Claims (6)
1. A device for connecting a combustion chamber to an injector in a thrust chamber, comprising: the combustion chamber of nonmetallic material is connected with the sprayer of metallic material, and the combustion chamber with shrink passageway is provided with the engaging lug with the sprayer link, and the combustion chamber passes through the front connection piece of sleeve and is connected with the sprayer, and the front connection piece of sleeve is by the front end suit of combustion chamber in the engaging lug outside of combustion chamber, and the rear connection piece of sleeve is by the rear end suit of combustion chamber in the rear side of the engaging lug of combustion chamber, front connection piece of sleeve and sleeve rear connection piece fixed connection.
2. A combustion chamber and injector connection in a thrust chamber as set forth in claim 1 wherein: the front connecting sheet of the sleeve is made of metal material, and the rear connecting sheet of the sleeve is made of metal material.
3. A combustion chamber and injector connection arrangement in a thrust chamber as claimed in claim 1 or 2, wherein: the front connecting piece of the sleeve and the rear connecting piece of the sleeve are welded by electron beams.
4. A combustion chamber and injector connection in a thrust chamber as set forth in claim 1 wherein: a sealing ring is arranged between the connecting lug and the front connecting sheet of the sleeve.
5. A combustion chamber and injector connection in a thrust chamber as set forth in claim 1 wherein: the section of the front connecting piece of the sleeve is -shaped, the upper part and the lower part of the -shaped front connecting piece of the sleeve are side walls, the side walls are sleeved on the outer sides of the connecting lugs, the left side is an end piece, and the end piece is annular; the rear connecting piece of the sleeve is annular.
6. A combustion chamber and injector connection in a thrust chamber as set forth in claim 5 wherein: the difference between the outer circle radius and the inner circle radius of the rear connecting sheet of the sleeve is larger than the wall thickness of the edge of the front connecting sheet of the sleeve.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311337307.6A CN117072346A (en) | 2023-10-17 | 2023-10-17 | Device for connecting combustion chamber and injector in thrust chamber |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311337307.6A CN117072346A (en) | 2023-10-17 | 2023-10-17 | Device for connecting combustion chamber and injector in thrust chamber |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117072346A true CN117072346A (en) | 2023-11-17 |
Family
ID=88704667
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311337307.6A Pending CN117072346A (en) | 2023-10-17 | 2023-10-17 | Device for connecting combustion chamber and injector in thrust chamber |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117072346A (en) |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB944355A (en) * | 1960-07-28 | 1963-12-11 | Gotex Ab | A solid propellant rocket motor and a method of manufacturing same |
| CN104234870A (en) * | 2014-06-13 | 2014-12-24 | 中国航天科技集团公司第六研究院第十一研究所 | Slotted coaxial pintle type injector thrust chamber |
| CN107956602A (en) * | 2017-11-23 | 2018-04-24 | 北京航天动力研究所 | A kind of new Joining Structure of composite thrust room |
| CN111022218A (en) * | 2019-12-31 | 2020-04-17 | 西北工业大学 | Hydrogen peroxide kerosene variable working condition thrust chamber adopting pintle injector |
| CN111502859A (en) * | 2020-04-29 | 2020-08-07 | 西北工业大学 | Initiating explosive-free gas-solid hybrid rocket engine |
| CN113074064A (en) * | 2021-05-10 | 2021-07-06 | 西安航天动力研究所 | NOFBX thrust chamber based on microchannel regenerative cooling technology |
| CN115726904A (en) * | 2022-09-07 | 2023-03-03 | 西安交通大学 | Thrust device of liquid rocket engine in composite cooling form |
-
2023
- 2023-10-17 CN CN202311337307.6A patent/CN117072346A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB944355A (en) * | 1960-07-28 | 1963-12-11 | Gotex Ab | A solid propellant rocket motor and a method of manufacturing same |
| CN104234870A (en) * | 2014-06-13 | 2014-12-24 | 中国航天科技集团公司第六研究院第十一研究所 | Slotted coaxial pintle type injector thrust chamber |
| CN107956602A (en) * | 2017-11-23 | 2018-04-24 | 北京航天动力研究所 | A kind of new Joining Structure of composite thrust room |
| CN111022218A (en) * | 2019-12-31 | 2020-04-17 | 西北工业大学 | Hydrogen peroxide kerosene variable working condition thrust chamber adopting pintle injector |
| CN111502859A (en) * | 2020-04-29 | 2020-08-07 | 西北工业大学 | Initiating explosive-free gas-solid hybrid rocket engine |
| CN113074064A (en) * | 2021-05-10 | 2021-07-06 | 西安航天动力研究所 | NOFBX thrust chamber based on microchannel regenerative cooling technology |
| CN115726904A (en) * | 2022-09-07 | 2023-03-03 | 西安交通大学 | Thrust device of liquid rocket engine in composite cooling form |
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| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |